BRPI0822244A2 - ''componentes estruturais de fuselagem de aeronave e método de produzir os mesmos'' - Google Patents

''componentes estruturais de fuselagem de aeronave e método de produzir os mesmos'' Download PDF

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Publication number
BRPI0822244A2
BRPI0822244A2 BRPI0822244A BRPI0822244A BRPI0822244A2 BR PI0822244 A2 BRPI0822244 A2 BR PI0822244A2 BR PI0822244 A BRPI0822244 A BR PI0822244A BR PI0822244 A BRPI0822244 A BR PI0822244A BR PI0822244 A2 BRPI0822244 A2 BR PI0822244A2
Authority
BR
Brazil
Prior art keywords
aircraft fuselage
members
frame members
stringer
producing
Prior art date
Application number
BRPI0822244A
Other languages
English (en)
Inventor
Augusto Eça Ferreira Clovis
Ferreira Fernadez Fernando
Donizette Aguiar José
Camargo Fortes Lucio
Galvão Do Prado Marcelo
Cruz Marcio
Takanashi Sadao
Original Assignee
Embraer Empresa Brasileira De Aeronautica S A
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Embraer Empresa Brasileira De Aeronautica S A filed Critical Embraer Empresa Brasileira De Aeronautica S A
Publication of BRPI0822244A2 publication Critical patent/BRPI0822244A2/pt
Publication of BRPI0822244B1 publication Critical patent/BRPI0822244B1/pt

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/061—Frames
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/064—Stringers; Longerons
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0081—Fuselage structures substantially made from particular materials from metallic materials
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49616—Structural member making
    • Y10T29/49622—Vehicular structural member making

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)

Abstract

componentes estruturais de fuselagem de aeronave e métodos de produzir os mesmos estruturas de fuselagem de aeronave apresentam membros de reforço na redondeza das aberturas de longarina formadas em membros de armação e são rigidamente unidas por junta sobreposta em uma região de superfície dos membros de armação por uma região de soldagem por fricção linear. tais componentes estruturais de fuselagem de aeronave podem, desse modo, serem fornecidos com uma pluralidade de membros de armação longitudinalmente afastados definindo um corte transversal de uma seção de fuselagem de aeronave, os membros de armação tendo uma pluralidade de orifícios de longarina nos mesmos, e uma pluralidade de longarinas orientadas longitudinalmente, cada uma estando posicionada dentro de um orifício de longarina respectivo dos orifícios de longarina do membro de armação. os membros de reforço são unidos por junta sobreposta a superfícies correspondentes dos membros de armação na redondeza dos orifícios da longarina tal que os membros de reforço sejam unidos rigidamente às superfícies correspondentes dos membros de armação por uma região de soldagem por fricção linear.
BRPI0822244-4A 2008-04-29 2008-12-05 'componentes estruturais de fuselagem de aeronave e método de produzir os mesmos BRPI0822244B1 (pt)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US12/111,825 2008-04-29
US12/111,825 US20090266936A1 (en) 2008-04-29 2008-04-29 Aircraft fuselage structural components and methods of making same
PCT/BR2008/000376 WO2009132402A2 (en) 2008-04-29 2008-12-05 Aircraft fuselage structural components and methods of making same

Publications (2)

Publication Number Publication Date
BRPI0822244A2 true BRPI0822244A2 (pt) 2019-10-08
BRPI0822244B1 BRPI0822244B1 (pt) 2020-12-01

Family

ID=41214045

Family Applications (1)

Application Number Title Priority Date Filing Date
BRPI0822244-4A BRPI0822244B1 (pt) 2008-04-29 2008-12-05 'componentes estruturais de fuselagem de aeronave e método de produzir os mesmos

Country Status (4)

Country Link
US (2) US20090266936A1 (pt)
EP (1) EP2280864B1 (pt)
BR (1) BRPI0822244B1 (pt)
WO (1) WO2009132402A2 (pt)

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EP2749491B1 (en) * 2012-12-28 2015-12-23 Airbus Operations, S.L. Aircraft structure with integrated reinforcing elements
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US9399510B2 (en) * 2014-08-20 2016-07-26 The Boeing Company Hat stringer closeout fitting and method of making same
US9927227B2 (en) 2014-09-17 2018-03-27 The Boeing Company Metrology system for generating measurements of fuselage sections
US11131982B2 (en) * 2014-09-17 2021-09-28 The Boeing Company Fuselage manufacturing system
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US11273930B2 (en) 2014-09-17 2022-03-15 The Boeing Company Cradle system for shaping fuselage sections
US10093406B2 (en) 2014-12-10 2018-10-09 The Boeing Company Aircraft frame for tailstrike angle enhancement
JP6212028B2 (ja) * 2014-12-26 2017-10-11 トヨタ自動車株式会社 点摩擦撹拌接合構造
EP3216691A1 (en) * 2016-03-07 2017-09-13 Airbus Operations GmbH Airframe component and methods for manufacturing an airframe component
US10220935B2 (en) * 2016-09-13 2019-03-05 The Boeing Company Open-channel stiffener
DE102016218431A1 (de) 2016-09-26 2018-03-29 Ford Global Technologies, Llc Verfahren zum Reparieren fehlerhafter Verbindungen
GB2575102A (en) * 2018-06-29 2020-01-01 Airbus Operations Ltd Duct stringer with bulkhead
CN112763166B (zh) * 2020-12-29 2023-04-14 中国航空工业集团公司西安飞机设计研究所 一种矩形机身舱体大开口结构侧向刚度确定方法
USD1016717S1 (en) * 2022-01-31 2024-03-05 Embraer S.A. Airplane

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Also Published As

Publication number Publication date
WO2009132402A2 (en) 2009-11-05
EP2280864B1 (en) 2018-04-25
US20130043346A1 (en) 2013-02-21
EP2280864A2 (en) 2011-02-09
EP2280864A4 (en) 2013-10-09
WO2009132402A3 (en) 2010-02-04
US8844871B2 (en) 2014-09-30
US20090266936A1 (en) 2009-10-29
BRPI0822244B1 (pt) 2020-12-01

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Legal Events

Date Code Title Description
B06F Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]
B25D Requested change of name of applicant approved

Owner name: EMBRAER S.A. (BR/SP)

B06U Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]
B09A Decision: intention to grant [chapter 9.1 patent gazette]
B16A Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]

Free format text: PRAZO DE VALIDADE: 10 (DEZ) ANOS CONTADOS A PARTIR DE 01/12/2020, OBSERVADAS AS CONDICOES LEGAIS.